Comprehensive task system compatible with multiple aerial carrier platforms

Abstract

A comprehensive task system compatible with multiple aerial carrier platforms mainly comprises a distribution board, a main control board, an external interface, a power supply module, a power supply switch and the like, integrates fire control and launch control, is designed in a highly integrated mode, is small in size, light in weight, good in electromagnetic compatibility, high in system matching performance and capable of being compatible with the multiple aerial carrier platforms for use. And a large amount of software and hardware research and development expenditure and personnel cost are reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of weapon launch control, and in particular to an integrated mission system compatible with multiple aircraft platforms. Background Art

[0002] In the mission system developed on the carrier platform, the conventional design mode of the fire control and launch control system is the design mode of flight control computer + mission computer + launch control box. The limitations of this mode are: in terms of hardware, the overall size of the system is large, the weight is heavy, and it occupies a large amount of the carrier platform load. The components need to be connected by external cables for power supply and communication, resulting in poor electromagnetic compatibility characteristics and high system power consumption. In terms of software, the entire system needs to develop three types of software and multiple communication protocols at the same time, and needs to undergo a large number of joint debugging tests to verify the overall performance of the system, and the funding and personnel costs are high. Summary of the invention

[0003] The present invention provides an integrated mission system compatible with multiple aircraft platforms, focusing on high reliability, miniaturization, and integrated design. It integrates three parts: a flight control computer, a mission computer, and a launch control box. It integrates fire control and launch control in one, and can complete multiple tasks such as pod control, launch envelope solution, navigation, external storage management, missile process control, and launch control.

[0004] The multi-carrier platform compatible integrated mission system provided by the present disclosure mainly includes: a power module, a power switch, a power distribution board, a main control board, an external interface and an internal cable network, wherein:

[0005] The power distribution board is used to supply power to the main control board and can control the power supply and launch of the missile according to the control instructions of the main control board;

[0006] A power module, used to provide power to the distribution board;

[0007] A power switch for controlling the supply of power to the distribution board;

[0008] The main control board is used to communicate with external airborne equipment and launch devices; to control the power distribution board to power and launch missiles according to the instructions of the control components; and to guide the aircraft flight, analyze fire control parameters, transmit firing parameters, control and launch missiles;

[0009] External interfaces include: interfaces with external airborne equipment and interfaces with missile launchers.

[0010] Furthermore, the power distribution board includes: an anti-backflow circuit, a missile power supply control circuit and a missile launch control circuit; wherein:

[0011] The anti-backflow circuit uses LM74700 and NMOS tube to build a reverse protection ideal diode circuit to complete the normal power supply and emergency power supply anti-backflow design;

[0012] The missile power supply control circuit uses the same four-way PMOS switch control circuit. The main control board controls the on and off of the PMOS tube, thereby controlling the missile power supply.

[0013] The missile launch control circuit uses the same four-way PMOS tube switch control circuit and four-way electromagnetic relay control circuit; under normal circumstances, the electromagnetic relay short-circuits the missile launch pyrotechnics to increase the safety of the entire system; the main control board controls the on and off of the PMOS tube and the switching of the electromagnetic relay, thereby controlling the missile launch.

[0014] Furthermore, the power module is a rechargeable lithium battery pack with a supply voltage range of 32V to 26V, which is charged by connecting to a carrier generator.

[0015] Furthermore, the power switch is a mechanical toggle switch.

[0016] Furthermore, the main control board adopts the STM32H7 minimum system, including:

[0017] The power supply circuit part is used to convert 28V power supply to 5V power supply, and then convert 5V power supply to 3.3V to supply power to the minimum system;

[0018] The off-chip components include: FLASH chip, reset circuit, A / D acquisition circuit, REF reference power supply circuit and crystal oscillator circuit;

[0019] The CPU adopts STM32H7 series chip and is equipped with KI / KO interface to output KO signal to the outside and collect KI signal. The KI signal includes: missile electrical separation signal and carrier lift-off status signal; the KO signal includes: missile power supply control signal and missile launch control signal. RS422 and CAN communication interfaces are also provided to complete information interaction with the outside.

[0020] Furthermore, in the main control board:

[0021] The KI and KO signals are isolated and converted from 28V to 3.3V signals through high-speed isolation optocouplers;

[0022] The RS422 communication circuit completes isolation conversion through isolation communication devices;

[0023] In the power circuit part, the first level uses a DC / DC isolated power module to convert the 28V power supply into an isolated 5V power supply, and the second level uses an LDO chip to convert 5V into 3.3V;

[0024] The power management chip is used to monitor the undervoltage and overvoltage of the CPU system's power supply in real time. It has an alarm accuracy of ±5% power window monitoring function and controls the power supply at 3.14V~3.46V; combined with the system power monitoring circuit and the AND gate device, it forms a CPU reset circuit.

[0025] Furthermore, the power circuit and the digital circuit in the main control board are arranged separately to improve the reliability of the internal system;

[0026] The high-power devices are placed on the back of the distribution board, so that the heat dissipation surface of the high-power devices and the bottom surface of the structural parts are in good contact, ensuring that the heat generated by the device is dissipated in time and keeping the entire system in a low thermal resistance state.

[0027] Furthermore, the system software is the main control board software, including: a bottom layer module, a basic module, a task module and a fault tolerance module, wherein:

[0028] The bottom-level modules are used for: (1) task management; (2) serial input / output; (3) analog input / output; (4) digital input / output; (5) timer / counter;

[0029] The basic module is used for: (1) judging on / off signals; (2) receiving communication data; (3) sending communication data; and (4) recording key signal status.

[0030] The mission module is used for: (1) real-time calculation of fire control / launch control parameters; (2) attack envelope navigation; (3) pod control; (4) missile launch process control;

[0031] The fault-tolerant module is used for: (1) initialization; (2) detection of master control failure; and (3) system switching / reorganization.

[0032] Further, the system also includes: airborne equipment, including: one or more of an airborne pod, a main inertial navigation, a control component, a display and control device, and an airborne data link;

[0033] The power module provides power to the airborne device, and the power switch controls the power supply to the airborne device.

[0034] Compared with the prior art, the beneficial effects of the present invention are: (1) small size, light weight, low system power consumption, cables are only connected inside the system shell, and the electromagnetic compatibility is good; (2) in terms of software, only one type of weapon interface unit main control software and one communication protocol need to be developed, the system has strong compatibility, and a large amount of R&D funds and personnel costs can be reduced; (3) fire control and launch control are integrated into one, and a highly integrated design is carried out, including searching for targets and automatically following, guiding aircraft flight, analyzing fire control parameters, transmitting shooting parameters, laser ranging and illumination, mounting, controlling and launching missiles and other functions; (4) only the mechanical interface required for the installation of the integrated mission system needs to be reserved on the carrier aircraft, and no carrier power supply and distribution is required, and no communication with the carrier aircraft platform is required; (5) it can be compatible with multiple carrier aircraft platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The above and other objects, features and advantages of the present disclosure will become more apparent through a more detailed description of exemplary embodiments of the present disclosure in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present disclosure.

[0036] Figure 1 A schematic diagram of a system structure according to an exemplary embodiment of the present disclosure;

[0037] Figure 2 is a schematic structural diagram of an exemplary switchboard;

[0038] Figure 3 This is a schematic diagram of the main control board;

[0039] Figure 4 A block diagram of an exemplary system configuration including external onboard devices. DETAILED DESCRIPTION

[0040] The preferred embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the preferred embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present disclosure more thorough and complete, and to fully convey the scope of the present disclosure to those skilled in the art.

[0041] The present disclosure provides an integrated mission system compatible with multiple aircraft platforms.

[0042] In an exemplary embodiment, the composition structure is as shown in the attached Figure 1 As shown in the figure, it consists of a power module, a power switch, a distribution board, a main control board, an external interface and an internal cable network. The main functions include:

[0043] 1) Control and operate components, display and control computers, main inertial navigation, pods, launchers and airborne data link power supply and distribution; 2) Control the power-on, alignment and launch of multiple missiles; 3) Receive and process instructions from control components; 4) Optoelectronic pod control function; 5) Missile launch safety insurance function; 6) Real-time calculation of fire control / launch control parameters; 7) Record flight data, fire control parameters and key signal status.

[0044] in:

[0045] (1) The power module is a rechargeable lithium battery pack with a supply voltage range of 32V to 26V. It can be connected to the aircraft generator for charging and can provide power for external components (including the pod, main inertial navigation, control components, display and control computer, and airborne data link) and the distribution board.

[0046] (2) The power switch is a mechanical toggle switch that can control the power supply to various components and distribution boards.

[0047] (3) Distribution board, principle block diagram as shown Figure 2 As shown, it is composed of an anti-backflow circuit, a missile power supply control circuit and a missile launch control circuit. It can supply power to the main control board and control the power supply and launch of the missile according to the control instructions of the main control board.

[0048] The anti-backflow circuit uses LM74700 and NMOS tube to build a reverse protection ideal diode circuit to complete the anti-backflow design of normal power supply and emergency power supply.

[0049] The missile power supply control circuit uses the same four-way PMOS tube switch control circuit. The main control board can control the on and off of the PMOS tube, thereby controlling the missile power supply.

[0050] The missile launch control circuit uses the same four-way PMOS tube switch control circuit and four-way electromagnetic relay control circuit. Under normal circumstances, the electromagnetic relay can short-circuit the missile launch pyrotechnics to increase the safety of the entire system. The main control board can control the on and off of the PMOS tube and the switching of the electromagnetic relay to control the missile launch.

[0051] (4) The main control board can communicate with external components and launch devices, and can control the power distribution board to power and launch missiles according to the instructions of the control components. The main control board mainly completes the functions of guiding the aircraft flight, analyzing fire control parameters, transmitting shooting parameters, and controlling and launching missiles.

[0052] As a preferred embodiment, the main control board in this embodiment is composed of the STM32H7 minimum system, and the principle block diagram is as follows: Figure 3As shown in the figure, the 28V power supply is converted to 5V power supply, and then the 5V power supply is converted to 3.3V to power the minimum system. The chip is composed of FLASH chip, reset circuit, A / D acquisition circuit, REF reference power supply circuit and crystal oscillator circuit. It outputs KO signal to the outside, collects KI signal, and forms RS422 and CAN communication interfaces to complete information exchange with the outside.

[0053] The KI and KO signals are isolated and converted from 28V to 3.3V through high-speed isolation optocouplers. High-speed transistor optocouplers are used, which have the characteristics of fast acquisition rate and short conversion time. The KI signal includes missile electrical separation signal, carrier aircraft lift-off status signal, etc. The KO signal includes missile power supply control, missile launch control, etc.

[0054] The first level of the power supply circuit uses a DC / DC isolated power supply module to convert the 28V power supply into an isolated 5V power supply, and the second level uses an LDO chip to convert 5V into 3.3V. The power management chip is used to monitor the undervoltage and overvoltage of the CPU system power supply in real time, with an alarm accuracy of ±5% power rail window monitoring function, and the power supply is controlled at 3.14V to 3.46V. Combined with the system power supply monitoring circuit, it is combined with the AND gate device to form a CPU reset circuit.

[0055] The CPU uses STM32H7 series chips, which have a higher main frequency, rich peripheral resources, and a power supply voltage of 3.3V.

[0056] The system uses an isolated RS422 communication circuit design to complete the isolation conversion through isolated communication devices. The RS422 signal uses the ADM2582E isolated RS422 transceiver, and the data transmission rate can reach 16Mbps.

[0057] (4) The system software is the main control board software, and the software architecture consists of the underlying module, basic module, task module and fault-tolerant module.

[0058] The specific functions of the bottom-level modules include: 1) task management function; 2) serial input / output function; 3) analog input / output function; 4) digital input / output function; 5) timing / counter function.

[0059] The specific functions of the basic module include: 1) on-off signal judgment function; 2) communication data receiving function; 3) communication data sending function; 4) key signal status recording function.

[0060] The specific functions of the mission module include: 1) real-time calculation of fire control / launch control parameters; 2) attack envelope navigation function; 3) pod control function; 4) missile launch process control function.

[0061] The specific functions of the fault-tolerant module include: 1) initialization function; 2) main control failure detection function; 3) system switching / reorganization function.

[0062] As a preferred embodiment, the present embodiment adopts the following optimized design:

[0063] Modular design: The modules are divided according to their functions, including power modules, power switches, distribution boards, main control board external interfaces and internal cable networks. The modules are interconnected through the internal cable network, which separates the power circuit and the digital circuit to improve the reliability of the internal system.

[0064] Thermal design: Place high-power devices on the back of the distribution board so that the heat dissipation surface of the high-power devices and the bottom surface of the structural parts are in good contact, ensuring that the heat generated by the device can be dissipated in time, so that the entire system remains in a low thermal resistance state, thereby improving the system's tolerance to high-altitude and low-temperature environments and improving working reliability.

[0065] This embodiment has the characteristics of small size and light weight. Its overall weight is about 3kg and its overall dimensions are about 300mm×160mm×80mm, which is convenient for installation on different aircraft platforms.

[0066] In addition, the system of this embodiment can also be used as a weapon interface unit, and by configuring more airborne equipment, a more complete mission system can be formed, such as the attached Figure 4 As shown:

[0067] The airborne equipment includes: a display and control computer, a control component, a main inertial navigation, a pod, a launcher, a data link system, external cables, etc. The weapon interface unit is connected to the control component, the display and control computer, the main inertial navigation, the pod, the launcher and the airborne data link through external cables;

[0068] The weapon interface unit contains a power module, which provides power to the control components, display and control computer, main inertial navigation, pod, launch device and airborne data link through external cables;

[0069] The weapon interface unit communicates in real time with the control components, display and control computer, main inertial navigation, pod, launch device and airborne data link through external cables.

[0070] in:

[0071] The control component can send relevant instructions to the weapon interface unit to control the missile power on, power off and launch. It can also control the pod to search for targets, automatically follow, laser ranging and illumination, etc.

[0072] The display and control computer can display pod video, fire control status, carrier aircraft status, target position, missile status, etc. in real time, and is also used to guide the pilot into the attack envelope.

[0073] The main inertial navigation adopts a combined navigation system to provide the system with relevant navigation parameters such as the aircraft's latitude and longitude, pitch angle, roll angle, true heading, magnetic heading, ground speed, and track angle.

[0074] The pod can search and monitor ground and air targets, lock onto targets and automatically track them; it can provide the system with accurate and real-time aiming line frame angular position and aiming line movement angular velocity; it is equipped with a laser light finder to measure the distance and illuminate the target, and can be used to guide laser missiles.

[0075] The data link system consists of an airborne data link terminal and a ground data link terminal, which enables the downlink of pod imaging information, missile information, target information and system working status between the airborne data link terminal and the ground data link terminal, and the uplink of remote control information.

[0076] The launch device is used to mount and release multiple missiles. It serves as a carrier platform to carry suspended objects and is installed at the weapon hanging point on the wing. It can reliably and stably suspend and carry air-to-ground missiles, and control the missile's power supply, communication and launch.

[0077] External cables are used to connect the weapon interface unit with the control components, display and control computer, main inertial navigation, pod, launch device and airborne data link.

[0078] The system workflow is divided into the ground self-check phase, the engine start-up phase and the aircraft flight phase, specifically:

[0079] (1) Ground self-check phase: The aircraft performs avionics check, the integrated mission system performs power-on check, and the pod and main inertial navigation system are aligned;

[0080] (2) Engine start-up phase: The aircraft conducts engine inspection and communication link check, and takes off after confirming that everything is normal;

[0081] (3) Aircraft flight phase: The pilot uses the control components to control the pod to search for and lock the target. The pilot controls the aircraft to enter the attack envelope according to the attack envelope displayed by the display and control computer. The pilot sends a command to power on the missile. The fire control computer controls the missile to power on and transmits the target data, aircraft position, and attitude data to the missile. It controls the missile to complete alignment and pre-launch checks. When the missile is ready, the pilot controls the pod to illuminate the laser, the pilot releases the missile, the missile leaves the rack, and the missile flies autonomously and hits the target.

[0082] The above technical scheme is only an exemplary embodiment of the present invention. For those skilled in the art, it is easy to make various types of improvements or modifications based on the application methods and principles disclosed in the present invention, and it is not limited to the method described in the above specific embodiment of the present invention. Therefore, the method described above is only preferred and does not have a restrictive meaning.

Claims

1. An integrated mission system compatible with multiple aircraft platforms, characterized in that: include: Distribution board, power module, power switch, main control board, external interface and internal cable network, including: The power distribution board is used to supply power to the main control board and can control the power supply and launch of the missile according to the control instructions of the main control board; A power module, used to provide power to the distribution board; A power switch for controlling the supply of power to the distribution board; The main control board is used to communicate with external airborne equipment and launch devices; to control the power distribution board to power and launch missiles according to the instructions of the control components; and to guide the aircraft flight, analyze fire control parameters, transmit firing parameters, control and launch missiles; External interfaces include: interfaces with external airborne equipment and interfaces with missile launchers.

2. The system according to claim 1, characterized in that The power distribution board includes: an anti-backflow circuit, a missile power supply control circuit and a missile launch control circuit; wherein: The anti-backflow circuit uses LM74700 and NMOS tube to build a reverse protection ideal diode circuit to complete the normal power supply and emergency power supply anti-backflow design; The missile power supply control circuit uses the same four-way PMOS switch control circuit. The main control board controls the on and off of the PMOS tube, thereby controlling the missile power supply. The missile launch control circuit uses the same four-way PMOS tube switch control circuit and four-way electromagnetic relay control circuit; under normal circumstances, the electromagnetic relay short-circuits the missile launch pyrotechnics to increase the safety of the entire system; the main control board controls the on and off of the PMOS tube and the switching of the electromagnetic relay, thereby controlling the missile launch.

3. The system according to claim 1, characterized in that The power module is a rechargeable lithium battery pack with a supply voltage range of 32V to 26V, and is charged by connecting to a carrier generator.

4. The system according to claim 1, characterized in that The power switch is a mechanical toggle switch.

5. The system according to claim 1, characterized in that The main control board adopts the STM32H7 minimum system, including: The power supply circuit part is used to convert 28V power supply to 5V power supply, and then convert 5V power supply to 3.3V to supply power to the minimum system; The off-chip components include: FLASH chip, reset circuit, A / D acquisition circuit, REF reference power supply circuit and crystal oscillator circuit; The CPU adopts STM32H7 series chip and is equipped with KI / KO interface to output KO signal to the outside and collect KI signal. The KI signal includes: missile electrical separation signal and carrier lift-off status signal; the KO signal includes: missile power supply control signal and missile launch control signal. RS422 and CAN communication interfaces are also provided to complete information interaction with the outside.

6. The system according to claim 5, characterized in that In the main control board: The KI and KO signals are isolated and converted from 28V to 3.3V signals through high-speed isolation optocouplers; The RS422 communication circuit completes isolation conversion through isolation communication devices; In the power circuit part, the first level uses a DC / DC isolated power module to convert the 28V power supply into an isolated 5V power supply, and the second level uses an LDO chip to convert 5V into 3.3V; The power management chip is used to monitor the undervoltage and overvoltage of the CPU system's power supply in real time. It has an alarm accuracy of ±5% power window monitoring function and controls the power supply at 3.14V~3.46V; combined with the system power monitoring circuit and the AND gate device, it forms a CPU reset circuit.

7. The system according to claim 1, characterized in that The power circuit and the digital circuit in the main control board are arranged separately to improve the reliability of the internal system; The high-power devices are placed on the back of the distribution board, so that the heat dissipation surface of the high-power devices and the bottom surface of the structural parts are in good contact, ensuring that the heat generated by the device is dissipated in time and keeping the entire system in a low thermal resistance state.

8. The system according to claim 1, characterized in that The system software is the main control board software, including: bottom module, basic module, task module and fault-tolerant module, among which: The bottom-level modules are used for: (1) task management; (2) serial input / output; (3) analog input / output; (4) digital input / output; (5) timer / counter; The basic module is used for: (1) judging on / off signals; (2) receiving communication data; (3) sending communication data; and (4) recording key signal status. The mission module is used for: (1) real-time calculation of fire control / launch control parameters; (2) attack envelope navigation; (3) pod control; (4) missile launch process control; The fault-tolerant module is used for: (1) initialization; (2) detection of master control failure; and (3) system switching / reorganization.

9. The system according to any one of claims 1 to 8, characterized in that: Also includes: Airborne equipment, including: one or more of an airborne pod, a main inertial navigation system, a control unit, a display and control device, and an airborne data link; The power module provides power to the airborne device, and the power switch controls the power supply to the airborne device.

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